JP2008519730A - Aircraft fuselage structure frame - Google Patents

Aircraft fuselage structure frame Download PDF

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JP2008519730A
JP2008519730A JP2007540690A JP2007540690A JP2008519730A JP 2008519730 A JP2008519730 A JP 2008519730A JP 2007540690 A JP2007540690 A JP 2007540690A JP 2007540690 A JP2007540690 A JP 2007540690A JP 2008519730 A JP2008519730 A JP 2008519730A
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lower arch
arch
fuselage
frame according
frame
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JP2008519730A5 (en
JP4524313B2 (en
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カッチャグェッラ．ブルーノ
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エアバス・フランス
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/18—Floors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B64C1/062—Frames specially adapted to absorb crash loads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Abstract

【課題】本発明の対象は、下部アーチ（１）、床部材（３）を支持する横梁（２）、および下部アーチ（１）と横梁（２）の間の連結格子（４）を含む胴体構造フレームである。
【解決手段】連結格子（４）は、端部が横梁（２）と下部アーチ（１）とに添え継ぎされたバー（４ａ、４ｂ）から構成することができる。
【選択図】図１An object of the present invention is a fuselage including a lower arch (1), a transverse beam (2) supporting a floor member (3), and a connecting grid (4) between the lower arch (1) and the transverse beam (2). It is a structural frame.
The connecting grid (4) can be composed of bars (4a, 4b) whose ends are spliced to the cross beam (2) and the lower arch (1).
[Selection] Figure 1

Description

本発明は、低質量でありながら大きな負荷を受けるようになされた床支持体を実現する航空機胴体構造フレームに関するものである。   The present invention relates to an aircraft fuselage structure frame that realizes a floor support that is designed to receive a large load while having a low mass.

航空機胴体構造は、胴体の軸に対して横方向に配置されたフレームを含み、フレームの下部は一般にアーチと呼ばれている。   An aircraft fuselage structure includes a frame disposed transverse to the fuselage axis, the lower portion of the frame being commonly referred to as an arch.

航空機が飛行中に、特にキャビン内部の与圧の作用により床面が変形する傾向に打ち勝つためには、航空機の船倉の床面など床支持体の横方向部材をフレームに連結することが望ましい。   In order to overcome the tendency of the floor surface to be deformed during the flight of the aircraft, particularly by the action of pressure inside the cabin, it is desirable to connect the transverse members of the floor support, such as the floor of the aircraft hold, to the frame.

本発明は、金属製アーチと、床支持体を形成する複合材横梁とを備えた構造を構成することにより、航空機の床支持手段を形成する航空機の構造フレームを実現するように特に適合されている。   The present invention is particularly adapted to realize an aircraft structural frame forming an aircraft floor support means by constructing a structure comprising a metal arch and a composite cross beam forming a floor support. Yes.

これを実現するため、本発明は主に、下部アーチと、床部材を支持する横梁と、下部アーチと横梁の間の連結格子とから成る、胴体構造フレームに関する。   In order to achieve this, the present invention mainly relates to a fuselage structure frame comprising a lower arch, a transverse beam supporting a floor member, and a connecting grid between the lower arch and the transverse beam.

横梁が下部アーチから遠ざけられ金属製または複合材の格子によりこのアーチに連結されるこの構成により、できる限り少ない質量および低いコストで、慣性がきわめて大きくかつきわめて背の高いフレームを作製することができ、下部構造は、フレーム全体の剛性に寄与する、横梁、格子、下部アーチから構成される。   This configuration, in which the cross beam is moved away from the lower arch and connected to the arch by a metal or composite grid, makes it possible to create a frame with very high inertia and very tall, with as little mass and low cost as possible. The substructure is composed of cross beams, lattices, and lower arches that contribute to the rigidity of the entire frame.

さらに、有利な実施例によれば、端部が横梁および下部アーチに添え継ぎされた複合材料製のバーから成る連結格子を使用することにより、胴体の外板と、構成部材（構造体またはシステム）が設置されているフレームの横梁との間の熱交換を最小限に抑えることができる。   Furthermore, according to an advantageous embodiment, the fuselage skin and the components (structure or system) are obtained by using a connecting grid consisting of composite bars with ends joined to the cross beam and the lower arch. ) Can minimize heat exchange with the horizontal beam of the frame in which it is installed.

本発明のその他の特徴および長所は、図面を参照して行う本発明の実施の非限定的な例についての以下の説明を読むことにより、よりよく理解されよう。   Other features and advantages of the present invention will be better understood by reading the following description of non-limiting examples of implementation of the invention made with reference to the drawings.

図１は、下部アーチ１、床部材３を支持する横梁２、および下部アーチ１と横梁２の間の連結格子４を含む胴体構造フレームの全体図である。   FIG. 1 is an overall view of a fuselage structure frame including a lower arch 1, a transverse beam 2 that supports a floor member 3, and a connecting grid 4 between the lower arch 1 and the transverse beam 2.

横梁２が下部アーチ１から間隔をおかれ格子４によりこのアーチに連結されるこの構成により、慣性がきわめて大きくきわめて背の高いフレームを作製することができる。   This arrangement in which the cross beam 2 is spaced from the lower arch 1 and connected to the arch by a lattice 4 makes it possible to produce a very tall frame with very high inertia.

下部構造は、横梁２と、端部が下部アーチ１および横梁２に添え継ぎされたバー４ａ、４ｂから成る格子４とを備え、下部アーチ１は床を完璧に支持し、フレーム全体を補剛し、したがってたとえば貨物飛行機構成に特に適合しており、横梁２と下部アーチ１との間に間隔を設け横梁２および格子４用に複合材を使用することにより、胴体の外板と、構成部材が設置されているフレームの横梁との間の熱交換を最小限に抑えることができる。   The substructure comprises a cross beam 2 and a lattice 4 consisting of bars 4a, 4b joined to the bottom arch 1 and cross beam 2 at the ends, the bottom arch 1 perfectly supports the floor and stiffens the entire frame Thus, for example, it is particularly adapted to a cargo plane configuration, for example, by providing a gap between the cross beam 2 and the lower arch 1 and using a composite for the cross beam 2 and the grid 4, so that the fuselage skin and components The heat exchange with the horizontal beam of the frame in which is installed can be minimized.

アーチと横梁を連結するために、上部フレーム部材５は、横梁２および下部アーチ１との連結用のアーム６ａ、６ｂ、７ａ、７ｂを備える。上部フレーム部材５および下部アーチ１は胴体構造のフレームの一部を成す。   In order to connect the arch and the cross beam, the upper frame member 5 includes arms 6 a, 6 b, 7 a, 7 b for connecting the cross beam 2 and the lower arch 1. The upper frame member 5 and the lower arch 1 form a part of a frame having a fuselage structure.

図１の例によれば、連結アーム６ａ、６ｂ、７ａ、７ｂは上部フレーム部材５の各端部にフォークを形成し、下部アーチ１および横梁２は添え継ぎにより各フォークのアーム６ａ、６ｂ、７ａ、７ｂに固定される。   According to the example of FIG. 1, the connecting arms 6a, 6b, 7a, 7b form a fork at each end of the upper frame member 5, and the lower arch 1 and the cross beam 2 are joined to each arm 6a, 6b, It is fixed to 7a, 7b.

横梁および下部アーチへのアームの固定は添え継ぎにより行われるが、アーム６ａを横梁２の端部に固定する例を図２ａに示す。   The fixing of the arm to the cross beam and the lower arch is performed by splicing. FIG.

この例によれば、下部アーチ１および横梁２は、当て金１１、１２およびボルト１３を用いた突き合せ添え継ぎにより、各フォークのアーム６ａ、６ｂ、７ａ、７ｂに固定される。   According to this example, the lower arch 1 and the cross beam 2 are fixed to the arms 6a, 6b, 7a, 7b of the respective forks by butt splicing using the stoppers 11, 12 and the bolts 13.

好ましい実施例においては、バー４は、図３に示すように、断面がＵ字形の複合材料製のビームであり、同じく複合材料製である横梁２は、この例によれば、ウエブ２ａの両端縁上に配置された方向が相対する２つの長手方向水平帯状部２ｂ、２ｃを備えた垂直ウエブ２ａの形態で作製され、帯状部のうちの一方は、帯状部２ｃのあらゆる歪みに対抗する折り返し唇状部２ｄとして自由端縁に設けることができる。   In the preferred embodiment, the bar 4 is a beam made of a composite material having a U-shaped cross section, as shown in FIG. 3, and the cross beam 2 also made of a composite material, according to this example, has both ends of the web 2a. Produced in the form of a vertical web 2a with two longitudinal horizontal strips 2b, 2c opposite in direction arranged on the edge, one of the strips being folded back against any distortion of the strip 2c The lip-shaped portion 2d can be provided at the free edge.

下部アーチ１は横梁２と同様、複合材料製のアーチとすることができるが、機械加工したアルミニウムアーチなど金属製のアーチとすることもできる。   The lower arch 1 can be a composite arch like the cross beam 2 but can also be a metal arch such as a machined aluminum arch.

下部アーチ１が金属製のアーチである場合、このアーチは、バーおよび上部フレームを固定する前に塗装され、バーと下部アーチの間の界面における腐食のリスクを回避するために、バー４ａ、４ｂの端部と下部アーチ１の間にガラス繊維クリース９が配置される。   If the lower arch 1 is a metal arch, this arch is painted before fixing the bar and upper frame, and bars 4a, 4b are used to avoid the risk of corrosion at the interface between the bar and the lower arch. A glass fiber crease 9 is disposed between the end of the arch and the lower arch 1.

図２ｂの例によれば、下部アーチ１は、胴体のパネル１４を支持する長手方向縦材８が通過する開口部１０を備えるリブ付きビームである。   According to the example of FIG. 2b, the lower arch 1 is a ribbed beam with an opening 10 through which a longitudinal longitudinal member 8 supporting the fuselage panel 14 passes.

図５は、縦材８と、フレーム同士を連結するロンジロン１６とを有する胴体部分の構造の実施図である。   FIG. 5 is an embodiment of the structure of the body portion having the vertical member 8 and the longilon 16 connecting the frames.

フレームは、胴体構造に沿って互いに間隔をおいて配置され、それらの長手方向の位置および胴体の形状に応じて寸法が異なる。   The frames are spaced apart from one another along the fuselage structure and have different dimensions depending on their longitudinal position and the shape of the fuselage.

本発明による胴体構造のフレームは、金属部材を用いて、あるいは金属−複合材料の混合構造によって作製するように適合され、複合材料製の格子は金属または複合材料のアーチに添え継ぎされる。   The frame of the fuselage structure according to the invention is adapted to be made with metal parts or with a mixed metal-composite structure, the composite grid being spliced to the metal or composite arch.

下部アーチ、上部フレーム部材、横梁、および連結格子の諸部材から成るアセンブリが全体の剛性に寄与する本発明は、図示の例に限定されるものではなく、特に図４は、上部フレーム部材が非対称型であり、アーム６ａ、６ｂを具備するフォークをその端部の一方に備え、単一固定プレート１５を別の端部に備える、変形例を示すものであり、アーチ、横梁、および連結格子の諸部材から成るアセンブリを複合材料製とするか、あるいは諸部材の少なくとも１つを金属製とし他の部材を複合材料製とすることができる。   The present invention in which the assembly comprising the members of the lower arch, the upper frame member, the cross beam, and the connecting grid contributes to the overall rigidity is not limited to the illustrated example. In particular, FIG. A fork with arms 6a, 6b at one of its ends and a single fixed plate 15 at its other end, showing a variation of the arch, cross beam and connecting grid The assembly of members can be made of composite material, or at least one of the members can be made of metal and the other member can be made of composite material.

本発明による胴体構造のフレームの正面図である。1 is a front view of a frame having a fuselage structure according to the present invention. 図１のフレームの詳細斜視図である。It is a detailed perspective view of the frame of FIG. 図１のフレームの詳細斜視図である。It is a detailed perspective view of the frame of FIG. 図１のフレームの格子の詳細斜視図である。FIG. 2 is a detailed perspective view of a lattice of the frame in FIG. 1. 本発明による上部フレーム部材の下部の拡大正面図である。It is an enlarged front view of the lower part of the upper frame member by this invention. 本発明による胴体構造の２つのフレームの斜視図である。2 is a perspective view of two frames of a fuselage structure according to the present invention. FIG.

符号の説明Explanation of symbols

１ 下部アーチ
２ 横梁
２ａ 垂直ウエブ
２ｂ，２ｃ 帯状部
２ｄ 唇状部
３ 床部材
４ 連結格子
４ａ，４ｂ バー
５ 上部フレーム部材
６ａ，６ｂ 連結アーム
７ａ，７ｂ 連結アーム
８ 縦材
９ ガラス繊維クリース
１０ 開口部
１１，１２ 当て金
１３ ボルト
１４ パネル
１５ 固定プレート
１６ ロンジロン DESCRIPTION OF SYMBOLS 1 Lower arch 2 Transverse beam 2a Vertical web 2b, 2c Strip | belt-shaped part 2d Lip-shaped part 3 Floor member 4 Connection grid 4a, 4b Bar 5 Upper frame member 6a, 6b Connection arm 7a, 7b Connection arm 8 Vertical member 9 Glass fiber crease 10 Opening Part 11, 12 Latch 13 Bolt 14 Panel 15 Fixing plate 16 Longon

Claims (10)

下部アーチ（１）、床部材（３）を支持する横梁（２）、および下部アーチ（１）と横梁（２）の間の連結格子（４）から成ることを特徴とする胴体構造フレーム。   A fuselage structure frame comprising a lower arch (1), a transverse beam (2) for supporting a floor member (3), and a connecting grid (4) between the lower arch (1) and the transverse beam (2). 前記連結格子（４）が、端部が横梁（２）と下部アーチ（１）とに添え継ぎされたバー（４ａ、４ｂ）から成ることを特徴とする請求項１に記載の胴体構造フレーム。   2. A fuselage structural frame according to claim 1, characterized in that the connecting grid (4) consists of bars (4a, 4b) whose ends are spliced to the cross beam (2) and the lower arch (1). バー（４）が、断面がＵ字形の複合材料製のビームであることを特徴とする請求項２に記載の胴体構造フレーム。   3. A fuselage frame according to claim 2, characterized in that the bar (4) is a beam made of a composite material having a U-shaped cross section. 上部フレーム部材（５）が、横梁（２）および下部アーチ（１）との連結アーム（６ａ、６ｂ、７ａ、７ｂ）を備え、下部アーチ（１）とともに胴体のフレームを形成することを特徴とする請求項１から３のいずれか１項に記載の胴体構造フレーム。   The upper frame member (5) is provided with connecting arms (6a, 6b, 7a, 7b) to the transverse beam (2) and the lower arch (1), and forms a fuselage frame together with the lower arch (1). The fuselage structure frame according to any one of claims 1 to 3. 連結アーム（６ａ、６ｂ、７ａ、７ｂ）が上部フレーム（５）の各端部にフォークを形成し、下部アーチ（１）および横梁（２）が添え継ぎにより各フォークのアーム（６ａ、６ｂ、７ａ、７ｂ）に固定されることを特徴とする請求項４に記載の胴体構造フレーム。   The connecting arms (6a, 6b, 7a, 7b) form a fork at each end of the upper frame (5), and the lower arch (1) and the cross beam (2) are joined to each fork arm (6a, 6b, The fuselage structure frame according to claim 4, wherein the fuselage structure frame is fixed to 7a, 7b). 下部アーチ（１）が、長手方向縦材（８）が通過する開口部（１０）を備えるリブ付きビームであることを特徴とする請求項１から５のいずれか１項に記載の胴体構造フレーム。   6. A fuselage structural frame according to claim 1, wherein the lower arch (1) is a ribbed beam with an opening (10) through which a longitudinal longitudinal member (8) passes. . 下部アーチ（１）が機械加工された金属製アーチであり、バー（４ａ、４ｂ）の端部と下部アーチ（１）の間にガラス繊維クリース（９）が配置されることを特徴とする請求項１から６のいずれか１項に記載の胴体構造フレーム。   The lower arch (1) is a machined metal arch, characterized in that a glass fiber crease (9) is arranged between the end of the bar (4a, 4b) and the lower arch (1). Item 7. The fuselage structure frame according to any one of Items 1 to 6. 下部アーチ（１）が複合材料製のアーチであることを特徴とする請求項１から６のいずれか１項に記載の胴体構造フレーム。   The fuselage structure frame according to any one of claims 1 to 6, characterized in that the lower arch (1) is an arch made of composite material. 下部アーチ（１）および横梁（２）が突き合せ添え継ぎにより各フォークのアーム（６ａ、６ｂ、７ａ、７ｂ）に固定されることを特徴とする請求項５に記載の胴体構造フレーム。   6. A fuselage structural frame according to claim 5, characterized in that the lower arch (1) and the cross beam (2) are fixed to the arms (6a, 6b, 7a, 7b) of each fork by butt splicing. 金属−複合材料の混合構造体により作製されることを特徴とする請求項１から９のいずれか１項に記載の胴体構造フレーム。   The fuselage structure frame according to any one of claims 1 to 9, wherein the frame is made of a mixed structure of metal and composite material.
JP2007540690A 2004-11-15 2005-11-07 Aircraft fuselage structure frame Expired - Fee Related JP4524313B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0452622A FR2877916B1 (en) 2004-11-15 2004-11-15 AIRCRAFT FUSELAGE STRUCTURE FRAME
PCT/FR2005/050932 WO2006051235A1 (en) 2004-11-15 2005-11-07 Structural frame for an aircraft fuselage

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JP2008519730A true JP2008519730A (en) 2008-06-12
JP2008519730A5 JP2008519730A5 (en) 2010-03-11
JP4524313B2 JP4524313B2 (en) 2010-08-18

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JP2007540690A Expired - Fee Related JP4524313B2 (en) 2004-11-15 2005-11-07 Aircraft fuselage structure frame

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US (1) US7874516B2 (en)
EP (1) EP1812288B1 (en)
JP (1) JP4524313B2 (en)
CN (1) CN100546872C (en)
AT (1) ATE403598T1 (en)
BR (1) BRPI0517861A (en)
CA (1) CA2585869C (en)
DE (1) DE602005008765D1 (en)
FR (1) FR2877916B1 (en)
RU (1) RU2357892C2 (en)
WO (1) WO2006051235A1 (en)

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WO2006051235A1 (en) 2006-05-18
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US7874516B2 (en) 2011-01-25
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US20080093503A1 (en) 2008-04-24
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ATE403598T1 (en) 2008-08-15
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BRPI0517861A (en) 2008-10-21
EP1812288B1 (en) 2008-08-06

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